The present disclosure relates to the technical field of space electric propulsion of spacecrafts, and discloses a thrust-quantitatively-controllable and self-neutralizable Kaufman ion thruster and a use method thereof. The Kaufman ion thruster includes a discharge chamber, a central cathode, a gas supply assembly, a steel magnetic assembly, an insulating barrier and a grid system, wherein the central cathode is coaxially inserted in the center of a front panel; the gas supply assembly includes an electronegative working substance gas source, a conventional working substance gas source, N electronegative working medium gas supply pipes and N working medium gas supply pipes; the insulating barrier includes a central connecting rod and 2N fins. Self-neutralization can be achieved without the need of neutralizers. In addition, the center-oriented thrust modes can be used for spacecraft orbit control; and the eccentric thrust mode can be used for spacecraft attitude adjustment.

Ionic thruster methods and apparatus for aircraft are disclosed. An example ionic thruster for aircraft includes a nozzle. The nozzle includes an outlet and an inlet, the inlet to receive fluid and containing an electrode mount. A ground electrode is disposed within the nozzle. Conducting pins are coupled to the electrode mount, each of the pins having a first end coupled to the electrode mount and a second end positioned closer to the ground electrode than the first end, the pins spaced apart from the ground electrode.

An electrospray emitter can include an emitter structure connected to a reservoir containing a working material in electrical communication with a first electrode and an electrode separated from an apex of the emitter structure by a distance, wherein a surface of the grid electrode proximal the emitter structure comprises at least one coating.

An electric ion propulsor and method of using is provided comprising a substrate having an inner surface and outer surface. A plurality of antennae mounted adjacent to each other on the inner surface and are enabled to transmit RF energy, and a controller having a connection to each of the plurality of antennae, a digital signal processor (DSP) and software stored in memory enabling control of transmission of the RF energy by each of the plurality of antennae. The antennae are subdivided into a plurality of arrays, a first array of the plurality of arrays serves to ionize ambient air and trap the resulting ionized air into a plurality of individual voxels and each voxel is transferred to another adjacent array, subsequently and in a linear direction, until the voxel exits the substrate at a speed enabling air movement causing thrust.

An integrated ion thruster unit for a spacecraft can include a unit housing including a thrust face, and a plurality of tiles arranged in an array on the thrust face. Each of the tiles can include an emitter and an extractor configured to provide a reference voltage with respect to the emitter. The emitter can include a plurality of tips configured to emit ions in a thrust direction from an ionic liquid propellant in response to an applied voltage.

Provided are an ion thruster and a fabrication method thereof. The method for fabricating the ion thruster comprises: stacking and laminating a plurality of prefabricated ceramic chips (p) to form a front portion (51); stacking and laminating a plurality of prefabricated green ceramic chips (p) to form a rear portion (B); assembling the front portion (51) and the rear portion (B) and placing in a sintering mold, and allowing the front portion (51) to be closely fitted with a tapered portion (b1) of the rear portion (B); placing a main cathode (1) into a cathode hole (k1) on the front portion and filling the cathode hole (k1) with a ceramic slurry to fix the main cathode (1); and placing the sintering mold in a heating furnace for sintering. For the ion thruster, a modular processing method is adopted. A method of stacking a plurality of prefabricated green ceramic chips (p) together and laminating them is used when each module is manufactured. The present application has the advantages of a simple process and low cost, and the fabricated ion thruster is small in size and has good high-temperature resistance.

Ionic thruster methods and apparatus for aircraft are disclosed. An example ionic thruster for aircraft includes a nozzle. The nozzle includes an outlet and an inlet, the inlet to receive fluid and containing an electrode mount. A ground electrode is disposed within the nozzle. Conducting pins are coupled to the electrode mount, each of the pins having a first end coupled to the electrode mount and a second end positioned closer to the ground electrode than the first end, the pins spaced apart from the ground electrode.